US9783283B2 - Fuselage equipment forming an access door and comprising a discharge control valve for pressurization air - Google Patents

Fuselage equipment forming an access door and comprising a discharge control valve for pressurization air Download PDF

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Publication number
US9783283B2
US9783283B2 US14/722,967 US201514722967A US9783283B2 US 9783283 B2 US9783283 B2 US 9783283B2 US 201514722967 A US201514722967 A US 201514722967A US 9783283 B2 US9783283 B2 US 9783283B2
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Prior art keywords
fuselage
flaps
aircraft
access
equipment
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US14/722,967
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US20150344123A1 (en
Inventor
Marc Tomasi
Patrick Lieven
Romain Delahaye
Matthieu De Kergommeaux
Laurent Lache
Didier Poirier
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Airbus Operations SAS
Airbus SAS
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Airbus SAS
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Assigned to AIRBUS OPERATIONS SAS reassignment AIRBUS OPERATIONS SAS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: De Kergommeaux, Matthieu, DELAHAYE, ROMAIN, LACHE, LAURENT, LIEVEN, PATRICK, POIRIER, DIDIER, TOMASI, MARC
Publication of US20150344123A1 publication Critical patent/US20150344123A1/en
Assigned to AIRBUS (SAS), AIRBUS OPERATIONS (SAS) reassignment AIRBUS (SAS) ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: AIRBUS OPERATIONS (SAS)
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • B64C1/1461—Structures of doors or surrounding frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • B64C1/1446—Inspection hatches
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised

Definitions

  • the invention relates to the field of aircraft fuselages. More specifically, it relates to items of fuselage equipment, and in particular access doors and valves for controlling pressurization.
  • an aircraft fuselage comprises one or more access hatches or doors which allow an operator, when this hatch/door is open, to enter the inside of the aircraft. It is, for example, an access door to an electronics bay (or “E Bay”) which is generally located in the lower portion of the fuselage. When it is open, this door leaves space for an access passage formed through the fuselage. This is because the standardized dimensions of this type of passage allow an operator to pass through, in order to reach the relevant compartment of the aircraft, from the outer side thereof.
  • the presence of the access passage also known as a “man hole,” requires a local reinforcement of the fuselage around this passage. This structural reinforcement is carried out by a thickening of the skin of the fuselage around the hole, and also using, for example, frames, side members, etcetera.
  • the fuselage is also provided with one or more pressurization control valves.
  • This valve is intended to allow control of the quantity of air which is discharged from a pressurized compartment of the aircraft, so that the pressure within this compartment is maintained at a safe level, and it remains comfortable for the passengers and the crew.
  • the cabin pressure controllers (“CPC”) which automatically control the quantity of air which is discharged via the dedicated valve.
  • the control valve is also mounted fixedly in a hole of the fuselage.
  • the fuselage therefore also has to be locally reinforced, using structural means which are identical or similar to those described above, in relation to the fitting of the access door.
  • the invention therefore proposes an item of equipment which is received in a single fuselage opening, in order to act as an access door and as a discharge control valve for pressurization air.
  • a single fuselage opening in order to act as an access door and as a discharge control valve for pressurization air.
  • only one opening is required through the fuselage in place of two. This involves only a single opening having to be reinforced structurally, which reduces the overall mass of the fuselage.
  • the invention preferably comprises at least one of the following optional features, taken in isolation or in combination.
  • the discharge control valve comprises two flaps which are articulated about two parallel rotation axes, respectively, the valve being configured to allow control of the discharge of the pressurization air by means of pivoting of the two flaps about the two rotation axes which remain fixed relative to the body of the item of equipment, the item of equipment also comprising the flaps in order to move them towards their access position, these movement means being configured so as to allow the two rotation axes to be moved apart when the flaps are moved towards their access position.
  • the item of equipment comprises means for locking the flaps in a control position.
  • the discharge control valve preferably comprises two movable flaps which define between them an opening which allows the discharge of pressurization air to be controlled. Alternatively, it may involve a single movable element, for example, of the flap type.
  • the invention also relates to an aircraft fuselage which comprises at least one item of equipment as described above, mounted in an opening of the fuselage.
  • the invention also relates to an aircraft which comprises such a fuselage, the item of equipment being mounted on a portion of the fuselage which delimits an electronics bay. Nonetheless, the equipment could be mounted on other portions of the fuselage, without departing from the scope of the invention.
  • the aircraft comprises means for controlling the discharge control valve for pressurization air, these means preferably being electrical control means.
  • the above-mentioned means for moving the flaps into their access position and/or the above-mentioned means for locking the flaps in a control position have electrical control means, these control means preferably being located in the cockpit of the aircraft.
  • FIG. 1 is a side view of an aircraft comprising a fuselage on which an item of equipment according to the invention is mounted;
  • FIG. 2 is a schematic cross section of the fuselage shown in the preceding Figure, the plane of section II-II designated in FIG. 1 passing through the equipment;
  • FIG. 3 is a perspective view of an item of equipment according to a first embodiment which is not covered by the invention but whose description will be given by way of information;
  • FIG. 4 is a bottom view of the equipment shown in FIG. 3 ;
  • FIGS. 5 a and 5 b schematically show the operation of a discharge control valve for pressurization air, mounted on the equipment shown in FIGS. 3 and 4 ;
  • FIG. 6 is a view similar to that of FIG. 4 , with the equipment in the form of a production alternative;
  • FIG. 7 is a sectioned view taken along the line VII-VII of FIG. 6 ;
  • FIG. 8 is a view similar to that of FIG. 4 , with the equipment in the form of a second preferred embodiment of the invention.
  • FIGS. 9 a and 9 b are sectioned views taken along the line IX-IX of FIG. 8 , with the equipment being in different configurations.
  • an aircraft 1 which comprises a wing 2 and a fuselage 4 .
  • it is a conventional transport airplane in the sense conventionally used by constructors in the field of aeronautics.
  • a space which is divided into two portions by a floor 6 which is arranged horizontally.
  • the upper space is generally dedicated to the fitting of the cockpit in the front portion of the aircraft and the passenger cabin at the rear portion.
  • the lower space is dedicated to the transport of goods and/or passenger baggage.
  • this compartment At the front of this compartment for transport of goods/baggage, there is generally provided a compartment which is referred to as an electronics bay 8 , in which there are installed a number of systems which are required for the correct operation of the aircraft. Therefore, there is generally provided an access door to this bay 8 below the level of the floor 6 , in order for one to be able to enter beneath this same bay and to carry out the operations required.
  • an electronics bay 8 In order for one to be able to enter beneath this same bay and to carry out the operations required.
  • an item of equipment 10 which is mounted on the fuselage and which allows access to this bay 8 from the outer side of the aircraft.
  • the equipment 10 specific to the present invention is arranged in the lower portion of the fuselage.
  • this equipment 10 not only acts as an access door to the electronics bay 8 , but also involves a discharge control valve for pressurization air.
  • This valve is intended to perform the conventional function thereof of controlling the quantity of air which is discharged via the pressurized bay 8 so that the pressure within this bay and within all of the pressurized compartments of the aircraft is maintained at a safe level and so that it remains comfortable for the passengers and the crew.
  • the control is carried out in an automatic manner by means of one or more cabin pressure controllers 14 which are electrical control means which are known per se and which are illustrated schematically in FIG. 1 .
  • FIGS. 3 to 5 b show a first embodiment which is not covered by the invention and in which the equipment 10 is an access door which is intended to be mounted in a fuselage opening 16 which is illustrated in FIG. 2 .
  • the equipment 10 is an access door which is intended to be mounted in a fuselage opening 16 which is illustrated in FIG. 2 .
  • it is an access door 10 which is articulated to the fuselage using hinges 33 .
  • this door 10 is therefore capable of releasing or blocking the opening 16 .
  • it could be a movable hatch which is mounted in the opening 16 , without departing from the scope of the invention.
  • the opening 16 when it is released by the opening of the access door 10 , forms an access passage which affords access to the inner side of the aircraft from the outer side thereof.
  • This access passage naturally complies with the standards in force, and thus has dimensions which are sufficient to allow the passage of an operator who wishes to enter the electronics bay 8 .
  • this type of passage 16 is generally of rectangular or square form.
  • the equipment 10 is therefore intended to block the access passage 16 when it is mounted on the fuselage 4 using hinges 33 and held in a closed position. It is also intended to release this same access passage 16 when it is moved into the open position by means of pivoting about hinges 33 , this pivoting preferably being carried out in a manual manner by an operator.
  • the equipment 10 comprises a body 20 which defines the contour of the door and on which there is mounted a device 22 for locking the door to the fuselage 4 , in the access passage 16 , this device 22 being manually controlled.
  • the locking device 22 has a conventional shape known to the person skilled in the art. It is, for example, a handle 24 which forms the manual control and which is connected to a linkage 26 which controls locking members 28 which protrude towards the outer side of the body 20 . These locking members 28 are intended to be introduced into corresponding holes formed in the fuselage 4 , in the region of the contour of the access passage 16 . Alternatively, the control of the locking members 28 could be electrical, without departing from the scope of the invention.
  • the manual actuation of the handle 24 by an operator, from inside the aircraft, allows the locking members 28 to be retracted or deployed depending on whether he wishes to lock or unlock the device 22 .
  • the equipment 10 is pivoted towards the inner side of the electronics bay 8 .
  • the body 20 is provided with abutment means 30 which protrude towards the outer side and which are intended to allow the equipment to be supported on the inner side of the fuselage when the equipment occupies the closed position thereof, as illustrated in FIGS. 2 to 4 .
  • these abutment means may be in the form of four support locations 30 which are arranged substantially close to the four rounded corners of the body 20 of the equipment.
  • a through-opening 32 in which the discharge control valve 34 for pressurization air is mounted. Therefore, when the equipment 10 which forms an access door is pivoted relative to the fuselage 4 in order to release the access passage 16 , this pivoting relates not only to the body 20 of the equipment, but also to the valve 34 which is mounted on the same body.
  • the invention is advantageous in that it requires only a single opening 16 through the fuselage for the performance of the two functions, that is to say, the access door to the electronics bay 8 and the discharge control valve 34 .
  • This affords advantages in terms of mass since only a single fuselage opening needs to be structurally reinforced, close to the periphery thereof.
  • this also allows the aerodynamic performance levels to be improved since, by providing a single fuselage opening in place of two, a potential source of drag which is linked with a potential misalignment between the skin of the fuselage and the outer surface of the equipment 10 mounted thereon is eliminated.
  • the invention also affords an advantage in terms of ease of production.
  • the discharge control valve 34 may be produced in any known manner by the person skilled in the art.
  • the configuration considered is of the type with two rotating flaps which are mounted so as to be articulated to the body 20 about parallel rotation axes 38 , these axes preferably being parallel with the transverse direction of the aircraft.
  • the two flaps 36 are positioned in an adjacent manner so that, in the closed position shown in FIG. 5 a , their opposing ends overlap each other in order to prevent the discharge of air between the two flaps.
  • an opening 40 is defined between these two opposing ends of the flaps so as to allow air to be discharged.
  • the extent of pivoting of the flaps 36 controls the passage cross-section of the opening 40 and thus allows the air pressure to be controlled inside the aircraft, as a result of the above-mentioned cabin pressure controllers.
  • the periphery of the body 20 is intended to incorporate sealing means in order to prevent leakages of air between this body and the access passage 16 provided through the fuselage 4 .
  • these sealing means of the lip seal type, could be provided on the access passage contour 16 .
  • the locking device 22 is itself preferably arranged at an end of the body 20 , while the control valve 34 is substantially centered on the same body.
  • the two movable flaps 36 of the control valve 34 are separated by the locking device 22 , which is substantially centered on the body 20 .
  • the control function is carried out via the two flaps 36 which each block a separate opening 40 through the body 20 , but the operation of these two flaps 36 is preferably not dissociated.
  • a return mechanism it is possible to retain a single motorization unit for controlling the two flaps 36 .
  • each flap is therefore in the form of a butterfly valve which, in accordance with the rotation thereof, releases an opening 40 which is formed through the body 20 .
  • an item of equipment 10 is shown in accordance with a second embodiment covered by the invention.
  • This item of equipment contrasts with those described above in that the body 20 thereof is intended to be mounted fixedly in the fuselage opening 16 , and is not intended to be articulated thereto. That is to say, it is no longer an access door, as was the case for the solutions described above, but an item of equipment 10 which is intended to remain permanently on the fuselage 4 , in the opening 16 thereof. Fixing means of the rivet or bolt type are therefore provided for the assembly of the body 2 in the opening 16 .
  • the control valve 34 is also mounted on the body 20 , with the two flaps 36 thereof articulated about the axes 38 , as shown in FIG. 8 and in FIG. 9 a in the closure position. In this position, the flaps 36 block an opening 32 which is produced through the body 20 so that the pressurization air cannot be discharged from the electronics bay.
  • this second embodiment involves the fact that the flaps 36 may be moved into a position which is referred to as the “access” position and which is indicated by the elements 36 ′′ in FIG. 9 b .
  • the flaps 36 ′′ are substantially vertical and release an access passage 16 ′ which affords access to the electronics bay of the aircraft.
  • the access passage 16 ′ released thereby corresponds to a large portion of the opening 32 which is formed through the body 20 and in which the valve 34 is mounted.
  • the movement from the closed position of the flaps 36 illustrated in FIG. 9 a to the access position 36 ′′ thereof shown in FIG. 9 b is preferably carried out using movement means 44 .
  • the means 44 are configured to apply to each flap 36 , relative to the body 20 , a movement which is different from a simple rotation of the flap 36 relative to the body 20 about the axis 38 thereof.
  • This movement is similar, for example, to a rotation whose axis which is parallel with the axis 38 is located on or close to the end of the flap which is arranged facing the contour of the opening 32 .
  • the movement means 44 are preferably configured to allow the two rotation axes 38 to be moved apart when the flaps 36 move from the closed position shown in FIG. 9 a to their access position 36 ′′ shown in FIG. 9 b . That is to say, the means 44 allow the rotation axes 38 to be moved relative to the body 20 of the item of equipment, while, in a configuration for simple control of discharge of pressurization air, these axes 38 remain fixed relative to the body 20 .
  • means 42 for locking the flaps 36 in a control position are preferably further provided. This is because these means 42 , which are carried by the fuselage 4 , allow the flaps 36 to be blocked in a position which permits them to pivot only about the axes 38 which therefore remain fixed relative to the body 20 of the equipment. Consequently, the flaps 36 cannot be displaced accidentally towards their access position which permits the passage of an operator.
  • These means 42 may, for example, be sliding bars which are capable of being inserted into their respective flaps 36 , for example, at two opposing ends of each flap, along the axis 38 . After the bars 42 have been withdrawn, the axes 38 of the flaps 36 are no longer blocked relative to the body 20 and these flaps may therefore be moved towards their access position 36 ′′ via the means 44 provided for this purpose.
  • electrical control means 14 ′ of the movement means 44 are provided in order to ensure the movement of the flaps into their access position 36 ′′ which affords the passage of an operator.
  • control means 14 ′ which can preferably be actuated from the cockpit and which control the sliding of the bars 42 which bring about the locking of the flaps 36 in a control position and the unlocking thereof.
  • the control means 14 , 14 ′ can be arranged within the same control module.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Power-Operated Mechanisms For Wings (AREA)
  • Air-Conditioning For Vehicles (AREA)
US14/722,967 2014-05-28 2015-05-27 Fuselage equipment forming an access door and comprising a discharge control valve for pressurization air Active US9783283B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1454818 2014-05-28
FR1454818A FR3021626B1 (fr) 2014-05-28 2014-05-28 Equipement de fuselage formant une porte d'acces et comprenant une vanne de regulation d'echappement d'air de pressurisation

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US20150344123A1 US20150344123A1 (en) 2015-12-03
US9783283B2 true US9783283B2 (en) 2017-10-10

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CN (1) CN105270600B (zh)
FR (1) FR3021626B1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10071815B2 (en) * 2016-03-28 2018-09-11 The Boeing Company Thrust recovery outflow valves for use with aircraft

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US3486721A (en) * 1967-07-26 1969-12-30 Ver Flugtechnische Werke Aircraft closure flaps
US3544045A (en) * 1969-01-10 1970-12-01 Garrett Corp Thrust recovery outflow control valve
US3740006A (en) * 1971-07-29 1973-06-19 Aircraft Corp Aircraft cabin outflow valve with torque reduction and noise abatement means
US4960249A (en) * 1988-05-27 1990-10-02 Abg Semca Controlled valve with possibility of autonomous opening and aircraft with a valve of this type
US5337977A (en) 1993-01-29 1994-08-16 The Boeing Company Vent-latch interlock assembly for an aircraft door
US6273136B1 (en) * 1998-03-25 2001-08-14 Nord-Micro Elektronik Feinmechanik Differential valve, specifically a cabin air discharge valve in an aircraft, and method for regulating cabin pressure
US7198062B2 (en) * 2002-11-21 2007-04-03 The Boeing Company Fluid control valve
FR2926534A1 (fr) 2008-01-21 2009-07-24 Airbus France Sas Porte d'aeronef pressurise equipe d'un volet de mise a l'air libre
US20100001127A1 (en) * 2008-07-04 2010-01-07 Markus Petrac Method for controlling the internal pressure in an aircraft
US20100096503A1 (en) * 2008-10-20 2010-04-22 Honeywell International Inc. Outflow valve having j-shaped bellmouth and cabin pressure control system employing the same
US20100216385A1 (en) * 2009-02-23 2010-08-26 Airbus Operations Gmbh Air Outlet Valve As Well As a System and Method for Emergency Ventilation of An Aircraft Cabin
US20110049299A1 (en) 2009-09-01 2011-03-03 Cessna Aircraft Company Aircraft Cabin Door Pressure Vent System
EP2428446A2 (en) 2010-09-09 2012-03-14 Honeywell International, Inc. Cabin pressure thrust recovery outflow valve with single door
US8376818B2 (en) * 2009-01-29 2013-02-19 Honeywell International Inc. Thrust recovery, or other valve, containing two independently actuated doors and control system

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US3426984A (en) * 1967-04-24 1969-02-11 United Aircraft Corp Aircraft pressurization outflow valve
DE19713125C2 (de) * 1997-03-27 1999-03-25 Nord Micro Elektronik Feinmech Verfahren zur Regulierung des Kabinendrucks in einem Fluggerät und Stufenventil hierfür
CN100408430C (zh) * 2003-08-28 2008-08-06 波音公司 流体控制阀，移动式平台和减小噪音的方法
DE102008056417B4 (de) * 2008-11-07 2010-11-11 Airbus Deutschland Gmbh Verfahren und System zur Notbelüftung einer Flugzeugkabine
US9475584B2 (en) * 2011-09-02 2016-10-25 Honeywell International Inc. Cabin pressure control system thrust recovery outflow valve and method that enable ram air recovery

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US3486721A (en) * 1967-07-26 1969-12-30 Ver Flugtechnische Werke Aircraft closure flaps
US3544045A (en) * 1969-01-10 1970-12-01 Garrett Corp Thrust recovery outflow control valve
US3740006A (en) * 1971-07-29 1973-06-19 Aircraft Corp Aircraft cabin outflow valve with torque reduction and noise abatement means
US4960249A (en) * 1988-05-27 1990-10-02 Abg Semca Controlled valve with possibility of autonomous opening and aircraft with a valve of this type
US5337977A (en) 1993-01-29 1994-08-16 The Boeing Company Vent-latch interlock assembly for an aircraft door
US6273136B1 (en) * 1998-03-25 2001-08-14 Nord-Micro Elektronik Feinmechanik Differential valve, specifically a cabin air discharge valve in an aircraft, and method for regulating cabin pressure
US7198062B2 (en) * 2002-11-21 2007-04-03 The Boeing Company Fluid control valve
US20100294887A1 (en) 2008-01-21 2010-11-25 Airbus Operations (Incorp. As A S.A.S) Pressurised aircraft door equipped with a vent flap
FR2926534A1 (fr) 2008-01-21 2009-07-24 Airbus France Sas Porte d'aeronef pressurise equipe d'un volet de mise a l'air libre
US20100001127A1 (en) * 2008-07-04 2010-01-07 Markus Petrac Method for controlling the internal pressure in an aircraft
US20100096503A1 (en) * 2008-10-20 2010-04-22 Honeywell International Inc. Outflow valve having j-shaped bellmouth and cabin pressure control system employing the same
US8376818B2 (en) * 2009-01-29 2013-02-19 Honeywell International Inc. Thrust recovery, or other valve, containing two independently actuated doors and control system
US20100216385A1 (en) * 2009-02-23 2010-08-26 Airbus Operations Gmbh Air Outlet Valve As Well As a System and Method for Emergency Ventilation of An Aircraft Cabin
US20110049299A1 (en) 2009-09-01 2011-03-03 Cessna Aircraft Company Aircraft Cabin Door Pressure Vent System
EP2428446A2 (en) 2010-09-09 2012-03-14 Honeywell International, Inc. Cabin pressure thrust recovery outflow valve with single door
US20120064813A1 (en) 2010-09-09 2012-03-15 Honeywell International Inc. Cabin pressure thrust recovery outflow valve with single door

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Also Published As

Publication number Publication date
CN105270600B (zh) 2019-06-18
FR3021626B1 (fr) 2017-12-22
FR3021626A1 (fr) 2015-12-04
CN105270600A (zh) 2016-01-27
US20150344123A1 (en) 2015-12-03

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